Fog arty
space delivery system

ABSTRACT

THE PRESENT DISCLOSURE RELATES TO A SPACE DELIVERY SYSTEM FOR DELIVERING ITEMS BETWEEN SPACE VEHICLES OR FOR COUPLING SPACE VEHICLES. THE DEVICE INVOLVES A FLEXIBLE EXTENSIBLE CABLE FED FROM A REEL AND THROUGH WHICH IS DELIVERED GAS TO THE FRONT OF THE CABLE WHERE IT IS DIRECTED BACKWARDLY TO PROPEL THE FRONT END OF THE CABLE FORWARDLY.

Jan. 29, 1974 c, P, FQGARTY Re. 27,903

SPACE DELIVERY SYSTEM 3 Sheets-Sheet 1 Original Filed Dec. 6. 1967 FIGJan. 29, 1974 FQGARTY Re. 27,903

SPACE DELI VERY SYSTEM Original Filed Dec. 6, 1967 3 Sheets-Sheet z Jan.29, 1974 c p FOGARTY Re. 27,903

SPACE DELIVERY SYSTEM 5 Sheets-Sheet s' Original Filed Dec. 6. 1967 FIGUnited States Patent Oflice Reissued Jan. 29, 1974 27,903 SPACE DELIVERYSYSTEM Charles P. Fogarty, Box 254, Commaclr, N.Y. 11725 Original No.3,478,986, dated Nov. 18, 1969, Ser. No. 691,107, Dec. 6, 1967, which isa continuation-in-part of abandoned Ser. No. 487,194, Sept. 14, 1965.Application for reissue Apr. 5, 1971, Ser. No. 131,044

Int. Cl. B64g 1/10 U.S. Cl. 244-1 SD 24 Claims Matter enclosed in heavybrackets appears in the original patent but forms no part of thisreissue specification; matter printed in italics indicates the additionsmade by reissue.

ABSTRACT OF THE DISCLOSURE The present disclosure relates to a spacedelivery system for delivering items between space vehicles or forcoupling space vehicles. The device involves a flexible extensible cablefed from a reel and through which is delivered gas to the front of thecable where it is directed backwardly to propel the front end of thecable forwardly.

The present specification is a continuation-in-part of Scr. No. 487,194,filed Sept. 14, 1965, now abandoned.

The present invention relates to a space delivery system and, moreparticularly, to a device for either coupling space vehicles together ortransferring items from one space vehicle to another.

Whereas space technology is now advanced to the stage where the linkingup of artificial satellites and other space vehicles is an essentialdesideratum, the present invention is concerned with the provision ofmeans for accomplishing the connection of such space members in apractical and highly effective manner or for delivering items from onespace member to another.

Accordingly an object of this invention is to provide for the transferof items from one space vehicle to another.

It is another object of the present invention to provide for thecoupling of a plurality of space vehicles or sections.

Another object of the present invention is to provide a method forcoupling a plurality of space vehicles or sections to the ends offacilitating the transference of cargo, personnel and the like from onecraft to another.

Another object of the present invention resides in the provision of amagnetic coupling system whereby one space vehicle may be towed byanother; whereby space stations may be assembled and whereby spacevehicles may be docked to a platform or station when required.

Another object of the invention is to provide a method for uniting twoobjects in space with expedience and control and with the obviation ofdifficulties concerning alignment and impact of said objects.

A further object of the instant coupling system is to provide meansfacilitating direct communication between space ships where said shipsare spacedly connected by cable means.

A still further object of this invention resides in the provision ofmeans facilitating the coupling and decoupling of space vehicles.

Another object of the present invention is to provide a life linebetween the space ships permitting the passage of personnel between saidships utilizing a connecting cable as a railing to prevent drift and forpermitting directional guidance.

Another object of the invention is the magnetic or other connection ofobjects relatively distant with respect to a space ship withoutnecessitating the movement of the ship or requiring personnel to departtherefrom.

Still another object of the instant invention is to permit thetransportation of a payload equivalent to the capacity of severalconventional vehicles carrying full loads whereby a vehicle equippedwith the present device would be coupled with a cargo ship ofsubstantially greater mass whereby the latter could be towed.

A further object of the invention disclosed herein is the provision oftow means capable of moving sections of space stations and the like tolocation and of aligning and connecting said sections with respect toeach other in a safe, positive and expedient manner.

A still further object of this invention resides in the provision ofmeans for retrieving magnetically attractable objects in space at aspecific location so that ships would not have to rendezvous but coulddump cargo which could subsequently be picked up by another ship.

Other objects of this invention will become apparent upon a morecomprehensive understanding of the invention for which reference is madeto the following specification and drawings and which describeillustrative embodiments of the invention and wherein:

FIGURE 1 is a perspective view of space vehicles connected by cableprior to being continguously coupled and a pick-up magnetic devicedepending from one of said vehicles;

FIGURE 2 is a plan view of space vehicles connected by respective pairsof magnet members;

FIGURE 3 is a perspective view of a space station and a space shipmagnetically and flexibly docked thereto;

FIGURE 4 is a perspective view of a plurality of space station sectionsbeing connected by the magnetic coupling system according to the presentinvention;

FIGURE 5 is a cross-sectional elevational view of an exemplary magnetharpoon or coupling means and motivation and retraction means associatedtherewith;

FIGURE 6 is a cross-sectional elevational view [of] exposing anexemplary electromagnetic harpoon or coupling means and the motivationand retraction means associated therewith;

FIGURE 7 is a cross-sectional elevational view similar to FIGURE 5 butshowing another type of grappling or coupling means;

FIGURE 8 is a cross-sectional elevational view similar to FIGURES 5 ad 7showing yet another means for grappling or for delivering an article;

FIGURE 9 is a cross-sectional elevational view similar to FIGURES 5-8showing human delivery means;

FIGURE 10 is a detailed perspective view of the plenum chamber of FIGS.5-8; [and] FIGURE 11 is a sectional view showing yet anotherembodiment[.]; and

FIGURE 12 is a schematic sectional view showing still anotherembodiment.

Referring now to the drawings wherein like reference numerals refer tolike or similar parts in the several figures, and more particularly toFIGURES 1 and 2, space vehicles 2 and 4 are shown respectively, inflexible and rigid coupled relation.

Essentially, flexible extensible cable generally designated by numeral 6is provided with a magnetic harpoon, or other suitable coupling,securing or grappling means, generally designated by the numeral 8connected at the free end thereof. Thus, when the term securing means"is used in the specification and claims it is meant to include any meanswhich will attach two objects together such as couplingor grapplingmeans. It is understood that many securing means require a correspondingmating element on the device to be secured thereto, such as thecooperative magnet members 40 and 44 as well as 42 and 46 of FIG. 2. Thecoupling means is movably connected to space vehicle 4 via said flexibleextensible cable, exemplary methods of carrying out such connection be-3 ing shown in FIGURES 5 and 6 of the accompanying drawings.

With specific reference to FIGURE 5, it will be seen that cable means 6is a flexible tubular member 7 and is connected at its end to a supplyof compressed gas 12, the latter being mounted within said space vehicle4. Cable 6 is windable on a two-way motor driven takeup reel 14, thelatter being referred to herein as retraction means. As shown in FIGURE5, a coupling means 8 is comprised preferably of a magnet, such aspermanent magnet 16, and a cylindrical plenum chamber 18 providedrearwardly of said magnet, nozzle orifices being provided as shown (noteFIGURE 10) wherethrough gas from said compresed gas supply 12 may becontrollably emitted upon regulation of control valve 22. Accordingly,it will be appreciated that gas emitted through said orifices willeffectuate directional propulsion of said harpoon means 8 outwardly ofsaid vehicle 6 and toward a designated target area as the motor driventakeup reel 14 unwinds the cable Z, such as target area being preferablya complementary magnetic connector means 24 provided on vehicle 2 asshown in FIGURE 1 of the accompanying drawings.

In place of magnetic coupling means 8 and 24, it should be understoodthat any suitable coupling means may be used. Thus, in FIGURE 7, insteadof providing the magnet 16 in front of the plenum chamber 18, agrappling hook 82 is provided which is capable of coupling with suitablemeans on the vehicle 2. If, instead of coupling, it is merely desired todeliver a suitable article from space vehicle 1 to space vehicle 2, sucharticle may be merely attached to the book 82 for delivery. It isparticularly advantageous to provide the leading face of the plenumchamber 18 with a connecting bracket 19 to which any desired couplingmeans may be attached.

In FIGURE 8 another type of delivery means is shown having attached infront of the plenum 18 via the connecting bracket 19, a rope holder 84to which is attached one end 86 of a rope 88 which forms a loop 87 atthe other end, the rope 88 slidably passing through the loop 87 andforming a lasso 89. An article to be delivered is merely snugglyretained in the noose and, upon reaching space vehicle 2, may be easilyremoved therefrom. An article may be retrieved from space by passing theopen lasso 89 to the article so that the article lies therewithin andthen winding up the hose 7 on the takeup reel 14 as described abovewhereby the lasso 89 will tighten about the article as shown in phantomin FIGURE 8. A weak and easily frangible retainer may be initiallyplaced within the lasso 89 to retain it in enlarged condition until thearticle is reached whereupon jerking of hose 7 will rupture thefrangible retainer and permit functioning as described.

FIGURE 9 shows yet another delivery system specifically adapted forcarrying an astronaut. Connected to the front of the plenum through auniversal joint 92 is a belt means 94 for passing about the astronautand snuggly retaining him in position. In such a delivery systent, it ispreferred to provide suitable means for the astronaut to hold onto, suchas the pair of handles 96 which are connected to the plenum by way ofthe connectors 98. The connectors 98 may be solid in which case only onesuch connector and handle 96 is needed for support and for steeringpurposes; however, as a further feature, it is preferred that controlmeans he built into the handles 96 so that the astronaut candirectionally propel himself. This is simply accomplished by providinghollow connecting means 98 and hollow handles 96 which hollow handleshave openings 100 therein, the handles 96 each being rotatably connectedto their respective connecting means 98. By rotating the handles 96 andthereby changing the position of the holes 100, the movement of theastronaut can be controlled by passage of gas through the openings 100.

The handle 96 can be replaced by a suitable fitting for connection toair actuated tools utilizing air from the plenum chamber. Further, thehollow connectors 98 may be used for housing communication lines runningfrom the vehicle through the cable 7 and plenum 18.

Further control means shown in FIGURE 11 may include further outwardlydirected openings 102; the openings 102 as well as the openings 20 beingprovided with valves 106 and 108, respectively, which may be opened andclosed at will by either the astronaut or from a remote location bysuitable electrical means (not shown) including radio-controlled means,if necessary. By opening and closing the desired valves, the directionof movement can be completely controlled. For remote location control,guiding lights 105 are provided, preferably one red and one green aparton the plenum 18 for assisting in directional propulsion control. Whenall the valves 106 are opened, the plenum will be stabilized. The valves106 are illustrated as being flap valves and valve 108 as being a rotaryvalve although it will be understood that any suitable valves may beused.

Another exemplary delivery means and associated structure, here shownutilizing a magnetic harpoon, is illustrated in FIGURE 6 and relates tothe preferred electromagnetic coupling means which, it will beappreciated can be controllably energized and dECl'lEIgiZCd. Flexibleextensible cable 6 is comprised of electrically conductive cable 25which carries power from battery 26 to electromagnet 28, said cablebeing windably receivable upon takeup reel 14, switch 30 being providedto enable controllable energization and deenergization of saidelectromagnet. Motivation of said electromagnet harpoon or couplingmeans is accomplished by the action of compressed gas which enterstubular member 32 via conduit 34 which is in communication withcompressed gas supply 12, and which expands against the enlarged end 36of shaft 38 of electromagnet 28. The gas, as aforedescribed with respectto the embodiment shown in FIGURE 5 hereof, is controlled by valve means[26] 22. Thus, harpoon means 28 may be motivated to positions distantwith respect to the space vehicle as designated in broken line in FIGURE6 of the drawings.

Consonant with the foregoing and with reference again to FIGURE 1, thecoupling means 8, the magnetic harpoon, is seen both in an approachingand contacting position with respect to space vehicle 2, flexibleextensible cable means 6 being connected intermediate said harpoon andspace vehicle 4. By retraction of said cable upon takeup reel 14 asshown in FIGURES 5 and 6, the vehicles 2 and 4 are drawn together asshown in FIGURE 2 of the drawings.

To the end of rigidly securing one space vehicle to the other subsequentto the retraction of coupling or securing means 8 which has been coupledusing the suitable grappling means, such as the magnetic connector,pairs of spaced grappling members, such as magnet members 40, 42 and 44,46, once permitted to assume relative proximity, draw said spacevehicles mutually toward one another until connection, such as by way ofmagnets, is effectuated. When magnets are used, the magnets of each pairof magnet members are of opposite polarity, i.e., magnet members 40 and46 being of north polarity and magnet members 42 and 44 being of southpolarity. Therefore, it will be observed, that by dint of theprearranged locations of said members on respective space vehicles andby reason of the polarity arrangement thereof, said vehicles will bemagnetically coupled in accordance with a predetermined orientation asshown in FIGURE 2.

Although the magnet members aforedescribed are arranged in pairspredeterminedly spaced in order that one pair will align and unite withthe other to effectuate a prearranged connection between the vehicles,it will be understood that said magnet members may be movable to permitvariation in the orientation achieved between vehicles. Thus, asillustrated in FIGURE 1 magnet member 44 shown in broken linedesignation, represents said member moved along track 48 and secured tothe space vehicle in an alternate position. Thus, by varying thepositions of said magnet members by any suitable means, said vehiclesmay be coupled in varying advantageous arrangements.

The coupling or securing means 50 movably connected to space vehicle 4via flexible extensible means 52 may structurally conform to theembodiments illustrated in aforedescribed FIGURES 5 and 6 utilizingmagnetic means, or other coupling or grappling means may be used such asshown in FIGURE 7. As indicated above, the purpose may be used to alignand unit space vehicles or may further include delivery, towing, pick-upof cargo, etc., in addition to the vehicle-coupling function describedwith respect to coupling means 8.

The coupling of other artificial space members in the manner hereinabovecharacterized with respect to space vehicles may be accomplished inaccordance with the present disclosure. Space station 60, e.g., shownassembled in FIGURE 3 and in the stages of assembly in FIG- DRE 4 isanother example whereby magnetic coupling means and magnet members maybe advantageously utilized. That is, magnet members 62, arrangedspacedly in pairs as shown, with the magnet members of each pair beingof opposite polarity, when mutually attached, retain space stationsections is connected, predetermined orientation. Magnetic couplingmeans 66 which is movably connected to one section 64 by flexibleextensible means 68, is propelled in a suitable manner towards a targetarea or magnetic connector means 70 provided on another section 64. Uponretraction of said flexible extensible means and coupling means, thetethered sections will be drawn together, the final assembledorientation of one section with respect to another being predeterminedin accordance with the positions of magnet members 62.

With further reference to FIGURE 3 of the drawings, it will be observedthat the concept of the present invention may be adapted to the dockingof space vehicles to space stations. Accordingly, space vehicle 2provided with the aforedescribed magnetic harpoon or coupling means atthe end of flexible cable or extensible means generally designated bynumeral 6, is thereby attached to a magnetic connector 80 located at oneend of the space station tower. By this method, the area otherwiserequired to land space craft has been eliminated and retrorockets wouldnot be required. Once the connection is accomplished, the vehicle may bepermitted to remain suspended or the cable may be retracted as describedherein whereby the vehicle may be caused to contact the tower.

The cable which may be tubular as described, may be used as a conduitthrough which materials may be transported from one space vehicle toanother. Electrical power, communications and the like may similarly becarried via such cables. The tubular member may be of telescopingconstruction and thus extensible and rigid as in FIGURE 12 wherein 101represents any suitable means for propelling and retrieving the securingmeans 103.

What is claimed is:

1. In a first artificial space member, the combination comprised ofmagnetic coupling means movably related with repsect to said spacemember, flexible extensible means connecting said coupling means withsaid space member, motivation means adapted to propel said couplingmeans to positions distant with respect to a side of said space member,retraction means capable of regulating the distance between saidcoupling means and said side of said space member from which saidcoupling means is adapted to be propelled the coupling means of saidfirst space member being adapted to magnetically unite with magneticconnector means provided on a second artificial space member wherebysaid first and second members may be proximately arranged uponretraction of said coupling means subsequent to the uniting of thelatter with said magnetic connector means and at least one pair ofspacedly disposed magnets provided on each space member, the magnets ofeach pair being of opposite polarity, a pair of magnets of one spacemember being arranged to align and unite with a pair of magnets ofanother space member whereby said space members will be magneticallycoupled in a predetermined orientation upon retraction of said couplingmeans subsequent to the uniting of the latter with said magneticconnector means.

2. A space station for use in outer space comprised of a plurality ofindividual sections, each respective section including at least one pairof spacedly disposed magnets provided thereon, the magnets of each pairbeing of opposite polarity, a pair of magnets of one section beingarranged to align and unite in outer space with a pair of magnets oranother section whereby said sections may be magnetically coupled in apredetermined orientation.

3. A space vehicle having a first pair of magnet members movablyattached to the body of said vehicle, said magnets being arrangedwhereby respective similarly facing poles thereof are of oppositepolarity, said magnet members being spacedly arranged with respect toone another and adapted to attract and attach to a second pair of spacedmagnet members provided on the body of another space vehicle, said firstand second pairs of magnet members, when mutually attached, beingadapted to retain said space vehicles in connected, predeterminedorientation.

4. In a space vehicle, the combination comprised of magnetic harpoonmeans and an extensible tubular member for use as a conduit means, saidtubular member movably connecting said harpoon means with said spacevehicle, motivation means adapted to propel said harpoon means topositions spaced with respect to said space vehicle, and retractionmeans capable of regulating the distance between said harpoon means andsaid space vehicle.

5. In a space vehicle as set forth in claim 4 including a compressed gassupply mounted within said space vehicle, said tubular member beingconnected at one end to said compressed gas supply and connected at theother end to said magnetic harpoon means.

6. In a space vehicle as set forth in claim 5 wherein said motivationmeans is comprised of nozzle orifices provided upon said harpoon means,said orifices being communicably connected to said tubular memberwhereby gas from said compressed gas supply can be controllably emittedthrough said orifices for directional propulsion of said magneticharpoon means.

7. A device in accordance with claim 5 wherein said magnetic harpoonmeans comprises an electromagnet.

8. A device for passage from one space vehicle to another comprisingsecuring means, a hollow plenum chamber behind said securing meanshaving exit apertures therein, a hollow flexible tubular conduit passingfrom said plenum chamber to a space vehicle, a reel for holding saidflexible condut wound thereabout, and a source of fluid pressureconnected to the end of said hollow conduit opposite said plenum chamberwhereby fluid pressure may be fed from said fluid pressure means throughsaid hollow conduit to said plenum chamber and out through the openingstherein to directionally propel said securing means away from said spacevehicle.

9. A device in accordance with claim 8 further comprising means tounwind and rewind said reel.

10. A device in accordance with claim 8 wherein said securing meanscomprises magnetic means.

11. A device in accordance with claim 8 wherein said securing meanscomprises a grappling hook.

12. A device in accordance with claim 8 wherein said securing meanscomprises a flexible lasso.

13. A device in accordance with claim 8 wherein said securing meanscomprises belt means mounted to said plenum chamber by way of auniversal joint.

14. A device in accordance with claim 8 wherein said securing meanscomprises astronaut holding means.

15. A device in accordance with claim 14 wherein said device furthercomprises means on said plenum chamber capable of steering saidastronaut.

16. A device in accordance with claim 8 wherein said securing meanscomprises article delivery means.

11. In a space vehicle, the combination comprised of securing means andan extensible tubular member for use as a conduit means, said tubularmember movably connecting said securing means with said space vehicle,motivation means adapted to propel said securing means to positionsspaced with respect to said space vehicle, and retraction means capableof regulating the distance between said securing means and said spacevehicle.

18. In a space vehicle as set forth in claim 17 including a compressedgas supply mounted within said space vehicle, said tubular member beingconnected at one end to said compressed gas supply and at the other endto said securing means, said motivation means comprising nozzle orificesprovided upon said securing means, said orifices being communicablyconnected to said tubular member whereby gas from said compressed gassupply can be controllably emitted through said orifices for directionalpropulsion of said securing means.

19. In a space vehicle as set forth in claim 18 wherein at least oneadditional orifice connected to said tubular member is connected to agas actuated tool for accomplishing Work in space.

20. In an artificial space object, the combination comprised of securingmeans and an extensible tubular member movably connecting said securingmeans with said space object, motivation means adapted to propel saidsecuring means to positions distant with respect to said space object,and means for retrieving said securing means.

21. In an artificial space object as set forth in claim 20 wherein saidextensible tubular member is rigid.

22. In an artificial space object as set forth in claim 21 wherein saidextensible rigid tubular member comprises a telescopic construction.

23. In an artificial space object as set forth in claim 20 wherein saidextensible tubular member is flexible.

24. In an artificial space object, the combination comprised of securingmeans and an extensible rigid telescoping member connected thereto,motivation means adapted to propel said securing means to positionsdistant with respect to said space object, and means for retrieving saidsecuring means.

References Cited The following references, cited by the Examiner, are ofrecord in the patented file of this patent or the original patent.

UNITED STATES PATENTS 2,359,964 10/1944 Barnett 114-168 X 2,471,6355/1949 Mark at al. 277- X 3,201,065 8/1965 Dunn 244-1 SD 3,285,53311/1966 Jernigan 244-1 SD OTHER REFERENCES Magnetic Forming in Space,Schwinghamer, Astronautics, September 1962, pp. 63-67.

Kamm, Satrac-Space Rendezvous System, Astronautics, June 1961, pp. 32,33, 44, 46.

GEORGE E. A. HALVOSA, Primary Examiner B. L. KELMACHTER, AssistantExaminer US. Cl. X.R. 244-1 SS

